ASTM F2317/F2317M-05(2007)
(Specification)Standard Specification for Design of Weight-Shift-Control Aircraft
Standard Specification for Design of Weight-Shift-Control Aircraft
ABSTRACT
This specification covers the minimum requirement for designing, testing, and labeling of weight-shift-control aircraft. This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces controlled by the pilot. Flight requirements are specified for: (1) proof of compliance including hang point and trimming setting; (2) general performance such as (a) stall speed in the landing configuration, (b) stall speed free of control limits, (c) minimum climb performance, (d) flutter, buffeting, and vibration, (e) turning flight and stalls, and (f) maximum sustainable speed in straight and level flight; (3) controllability and maneuverability such as general, longitudinal, and lateral control; and (4) longitudinal stability and pitch testing. Structural requirements specified include: (1) strength requirements, (2) fulfillment of design requirements, (3) safety factors, (4) design airspeeds, (5) flight loads, (6) pilot control loads, (7) ground loads including landing gear shock absorption, and (8) emergency landing loads. Design and construction requirements are specified for: (1) materials, (2) fabrication methods, (3) self-locking nuts, (4) protection of structure, (5) accessibility, (6) setup and breakdown, (7) control system evaluated by operation test, (8) mast (pylon) safety device, (9) cockpit design, and (10) markings and placards. Powerplant requirements including installation, fuel system, oil system, induction system, and fire prevention, as well as equipment requirements such as powerplant instruments, miscellaneous equipment, and lap belts and harnesses, are detailed. Operating limitations such as load distribution limits are also specified.
SCOPE
1.1 This specification covers the minimum airworthiness standards a manufacturer shall meet in the designing, testing, and labeling of weight-shift-control aircraft.
1.2 This specification covers only weight-shift-control aircraft in which flight control systems do not use hinged surfaces controlled by the pilot.
Note 1—This section is intended to preclude hinged surfaces such as typically found on conventional airplanes such as rudders and elevators. Flexible sail surfaces typically found on weight-shift aircraft are not considered hinged surfaces for the purposes of this specification.
1.3 Weight-shift-control aircraft means a powered aircraft with a framed pivoting wing and a fuselage (trike carriage) controllable only in pitch and roll by the pilot's ability to change the aircraft's center of gravity with respect to the wing. Flight control of the aircraft depends on the wing's ability to flexibly deform rather than the use of control surfaces.
1.4 This specification is organized and numbered in accordance with the bylaws established for Committee F37. The main sections are: Scope1 Referenced Documents2 Terminology3 Flight Requirements4 Structural Requirements5 Design and Construction Requirements6 Powerplant Requirements7 Equipment Requirements8 Operating Limitations9 Keywords10 AnnexAnnex A1 AppendixAppendix X1
1.5 The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in non-conformance with the standard.
1.6 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory requirements prior to use.
General Information
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Standards Content (Sample)
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Designation: F 2317/F 2317M – 05 (Reapproved 2007)
Standard Specification for
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Design of Weight-Shift-Control Aircraft
This standard is issued under the fixed designation F2317/F2317M; the number immediately following the designation indicates the
year of original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last
reapproval. A superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope priate safety and health practices and determine the applica-
bility of regulatory requirements prior to use.
1.1 This specification covers the minimum airworthiness
standards a manufacturer shall meet in the designing, testing,
2. Referenced Documents
and labeling of weight-shift-control aircraft.
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2.1 ASTM Standards:
1.2 This specification covers only weight-shift-control air-
F2339 Practice for Design and Manufacture of Reciprocat-
craftinwhichflightcontrolsystemsdonotusehingedsurfaces
ing Spark Ignition Engines for Light Sport Aircraft
controlled by the pilot.
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2.2 Federal Aviation Regulations:
NOTE 1—This section is intended to preclude hinged surfaces such as
FAR-33 Airworthiness Standards: Aircraft Engines
typically found on conventional airplanes such as rudders and elevators.
FAR-35 Airworthiness Standards: Propellers
Flexible sail surfaces typically found on weight-shift aircraft are not
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2.3 Joint Aviation Requirements:
considered hinged surfaces for the purposes of this specification.
JAR-E Engines
1.3 Weight-shift-control aircraft means a powered aircraft
JAR-P Propellers
with a framed pivoting wing and a fuselage (trike carriage)
JAR-22 Sailplanes and Powered Sailplanes
controllable only in pitch and roll by the pilot’s ability to
change the aircraft’s center of gravity with respect to the wing. 3. Terminology
Flight control of the aircraft depends on the wing’s ability to
3.1 Definitions—Aircraft Weight:
flexibly deform rather than the use of control surfaces.
3.1.1 design maximum aircraft weight, n—aircraft design
1.4 This specification is organized and numbered in accor-
maximum weight W shall be the sum of W + W .
MAX WING SUSP
dance with the bylaws established for Committee F37. The
3.1.2 design maximum trike carriage weight, n—design
main sections are:
maximum trike carriage weight, W , shall be established so
susp
Scope 1
that it is: (1) highest trike carriage weight at which compliance
Referenced Documents 2
with each applicable structural loading condition and each
Terminology 3
Flight Requirements 4 applicableflightrequirementisshown,and(2)notlessthanthe
Structural Requirements 5
empty trike carriage weight, W , plus a weight of occu-
tkmt
Design and Construction Requirements 6
pant(s)of86.0kg[189.6lb]forasingle-seataircraftor150kg
Powerplant Requirements 7
Equipment Requirements 8 [330.8 lb] for a two-seat aircraft, plus the lesser of full usable
Operating Limitations 9
fuel or fuel weight equal to 1-h burn at economical cruise at
Keywords 10
maximum gross weight.
Annex Annex A1
Appendix Appendix X1 3.1.3 trike carriage empty weight, W , n—all parts, com-
tkmt
ponents, and assemblies that comprise the trike carriage
1.5 The values stated in either SI units or inch-pound units
assembly or that are attached to the suspended trike in flight,
are to be regarded separately as standard. The values stated in
including any wing attachment bolts, shall be included in the
each system may not be exact equivalents; therefore, each
trike carriage assembly empty weight, W . These must
tkmt
system shall be used independently of the other. Combining
include the required minimum equipment, unusable fuel,
values from the two systems may result in non-conformance
maximum oil, and where appropriate, engine coolant and
with the standard.
1.6 This standard does not purport to address all of the
safety concerns, if any, associated with its use. It is the
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responsibility of the user of this standard to establish appro-
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
Standards volume information, refer to the standard’s Document Summary page on
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This specification is under the jurisdiction of ASTM Committee F37 on Light the ASTM website.
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Sport Aircraft and is the direct responsibility of Subcommittee F37.40 on Weight Available from Federal Aviation Administration, 800 Independence Ave., SW,
Shift. Washington, DC 20591.
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Current edition approved Dec. 1, 2007. Published September 2008. Originally Available from Global Engineering Documents, 15 Inverness Way, East
approved in 2005.Lastprevious edition approved in 2005 as F2317/F2317M–05. Englewood, CO 80112-5704
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United
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